AE 60022 AE 40030 ADVANCED GAS TURBINE THEORY Dr. Chetan S. Mistry Lecture-1 ADVANCED GAS TURBINE THEORY AE 60022 / AE 40030 ADVANCED GAS TURBINE THEORY 1. General propulsion systems, 1. Introduction to Jet Propulsion systems 2. Theory of intakes and exhaust systems, thrust reversers, 2. Types of aircraft engines 3. Jet engine noise and methods of noise 3. Jet engine Thermal Cycle analysis reduction, 4. Two spool and Three spool configurations 4. Cycle analysis of one and two spool 5. Engine Installation & Theory of Intakes engines, 6. Exhaust nozzles 5. Equilibrium running of gas turbine engines, 7. After burners and Thrust reverser 6. Design and off-design performance, 8. Design considerations for axial flow Component matching, Transient behaviour, turbomachines 7. Design consideration of axial flow 9. Design and off-design performance multistage machines, stream line curvature 10.Component matching method, radial equilibrium equation Dr. Chetan S. Mistry Course Pre-requisites Introduction to Aerospace Propulsion, or A course in Engineering Thermodynamics Additionally : A course in Fluid Mechanics and Gas dynamics would be helpful Dr. Chetan S. Mistry Work Ethics • DO participate and ask questions. For order in class, raise your hand when asking a question. • BRING all specified ENGINEERING equipment like Notebook, Calculator, Gas table. • HAND IN all Assignments ON TIME! Failure to do so may result in consequences…YOU KNOW.. • SHOW CARE and concern for each other. Help one another in homework. BUT NO COPYING OF ENTIRE ASSIGNMENTS! • Design projects--- Group work • IF you are LATE in class Do not take permission….. Take your seat without disturbing whole class. • Attendance---- Be Physically and Mentally present. Dr. Chetan S. Mistry Dr. Chetan S. Mistry Course Evaluation Examination Scheme Teaching Component Scheme Hours Course Weightage Course Name Code Hours / CE Week C SEE MS + ES LTP Att. AE60022 ADVANCED GAS 3 ‐ 03 3 0.20 0.30 0.50 AE 40030 TURBINE THEORY Dr. Chetan S. Mistry Weekly -3 Lectures 1. Introduction to Propulsion systems 2. Types of aircraft engines 4 Lectures 3. Jet engine Thermal Cycle analysis 7 Lectures 4. Two spool and Three spool configurations 5. Engine Installation &Theory of Intakes 8 Lectures 6. Exhaust nozzles 8 Lectures 7. After burners and Thrust reverser 8. Design considerations for axial flow 6 Lectures turbomachines 9. Design and off-design performance 7 Lectures 10.Component matching Dr. Chetan S. Mistry Text/References 0. Class notes / Lecture notes 1. Saravanamuttoo, H.I.H., Rogers G.F.C., Cohen H.; Gas Turbine Theory, 2001, Pearson 2. El-Sayed Ahmed, Aircraft Propulsion and gas Turbine Engines , 2008, T&F,CRC press. 3. Saeed Farokhi, Aircraft Propulsion, 2009, John Wiley & Sons, Inc. 4. Kaluse Hunecke , Jet Engines-Fundamentals of theory, design and Operation, Motor books International 5. Hill Philip, Peterson Carl, Mechanics and Thermodynamics of Propulsion, 1992, Addison Wesly 6. Mattingly J D , Elements of Propulsion – Gas Turbines and Rockets, 2006, AIAA Education series. 7. Mattingly J D , Aircraft engine design, 2006, AIAA Education series. 8. Gordon C. Oates, Aircraft Propulsion Systems Technology and Design, 1989, AIAA Education series. 9. Roy Bhaskar, Aircraft Propulsion, 2008, Elsevier (India) Dr. Chetan S. Mistry Aerospace Engines Air breathing Non-Air breathing Engines Engines Reciprocating Jet propulsion engines engines Ramjet Scramjet Pulsejet Gas turbine Turbo ramjet Turbo rocket or Jet engine Dr. Chetan S. Mistry Jet Engines Turbojet Turboprop Turboshaft Turbofan Unducted Ducted fan Propfan Engine Non A/B With A/B Propeller/ Rotor Industrial Single Counter rotating On Compressor turbine shaft propeller fan propeller fan Propeller/ Rotor Driven by free Turbine Next Slide Dr. Chetan S. Mistry Turbofan Engines Forward fan Aft fan Advanced ducted fan High Bypass Low Bypass Mixed flow Unmixed flow ratio ratio Non afterburning Afterburning Non A/B With A/B Single spool Geared fan Two spool Ungeared fan Three spool Dr. Chetan S. Mistry Evolution of aero engines. Dr. Chetan S. Mistry Lecture-2 ADVANCED GAS TURBINE THEORY Turbojet Engine After burner Number of spools With After Without After Single spool Two spool burner burner Axial flow Centrifugal Axial-Centrifugal compressor compressor compressor Dr. Chetan S. Mistry Single spool Turbojet Engine CC Nozzle Diffuser Turbine Compressor J85‐GE‐17A turbojet engine from General Electric (1970) Dr. Chetan S. Mistry Dr. Chetan S. Mistry Single spool Turbojet Engine Westinghouse J34 Dr. Chetan S. Mistry Single spool Turbojet Engine Double spool Turbojet Engine MIG23 afterburner Dr. Chetan S. Mistry Why afterburner ? • After burning (reheat) method which augmenting the basic thrust of engine. • Increasing thrust without adding extra weight or complexity • Improve aircraft takeoff, climb and combat performance for supersonic aircraft. With Without afterburning afterburning Altitude time Dr. Chetan S. Mistry Turbojet Engine • Use of high exhaust gas velocity increases the Thrust developed by the engine. • Simplicity of design, • Efficient at supersonic speed. • Improvement in efficiency. • SFC • Power at supersonic flight. ???? • Noise Dr. Chetan S. Mistry Lecture-3 ADVANCED GAS TURBINE THEORY Turbofan Engines Forward fan Aft fan High Bypass Low Bypass Mixed flow Unmixed flow ratio ratio Non afterburning Afterburning Non A/B With A/B Single spool Geared fan Two spool Ungeared fan Three spool Dr. Chetan S. Mistry Single-spool Turbofan engine Combustion Compressors Turbines Chamber Nozzle/Exhaust Inlet Bypass airflow Bypass ratio Primary airflow m Cold m Hot m fan m core •At nozzle exit, fluid flow at primary and secondary nozzle are mixed. Optional: Afterburner, Convergent or Con/Di Nozzle Dr. Chetan S. Mistry Two spool turbofan - Low bypass ratio Divergent Air Intake Nozzle LP Compressors LP Turbines Burner HP Compressors HP Turbine Dr. Chetan S. Mistry Maximum Thrust: takeoff thrust: 2,050 lbf (9.1 kN) OPR: 24 BR: 2.9 SFC: <0.7 lb/lbf/h (20 g/kN/s) T‐to‐W: >5 GE Honda HF120 Aero Engine Dr. Chetan S. Mistry.